GLAST Mission Overview. Delta II 7920H-10 Cape Canaveral Air Force Station, FL Space Launch Complex-17B

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1 GLAST Mission Overview Delta II 7920H-10 Cape Canaveral Air Force Station, FL Space Launch Complex-17B

2 GLAST United Launch Alliance is proud to launch the Gamma-ray Large Area Space Telescope (GLAST) mission. GLAST will be launched aboard a Delta II 7920H-10 launch vehicle from Cape Canaveral Air Force Station (CCAFS), Florida. The launch will deliver the GLAST observatory into a circular orbit around the Earth where it will look into the galaxy to study powerful gamma-ray phenomena such as neutron stars and black holes; cosmic rays that interact with interstellar gas and dust in the galaxy; the diffuse extragalactic background, supernovae; and mysterious gamma-ray bursts. United Launch Alliance provides the Delta II launch service under the NASA Launch Services (NLS) contract with the NASA Kennedy Space Center Launch Services Program (LSP). We are delighted that NASA has chosen the Delta II for this mission. I congratulate the entire Delta team for their significant efforts that resulted in achieving this milestone and look forward to continued launches of scientific space missions aboard the Delta launch vehicle. Kristen T. Walsh Director, NASA Programs Delta Launch Vehicles

3 GLAST Mission Overview The Universe is home to numerous exotic and beautiful phenomena, some of which can generate almost inconceivable amounts of energy. Supermassive black holes, merging neutron stars, streams of hot gas moving close to the speed of light these are but a few of the marvels that generate gamma-ray radiation, the most energetic form of radiation, billions of times more energetic than the type of light visible to our eyes. The Gamma-ray Large Area Space Telescope (GLAST) will open this high-energy world to exploration. With GLAST, astromoners will have a superior tool to study how black holes, notorious for pulling matter in, can accelerate jets of gas outward at fantastic speeds. Physicists will be able to study subatomic particles at energies far greater than those seen in ground-based particle accelerators. Cosmologists will also gain valuable information about the birth and early evolution of the Universe.

4 GLAST Science Objectives Explore the most extreme environments in the Universe where nature harnesses energies far beyond anything possible on Earth. Search for signs of new laws of physics and what composes the mysterious dark matter. Explain how black holes accelerate immense jets of material to nearly light speed. Help crack the mysteries of the stupendously powerful explosions known as gamma-ray bursts. Answer long-standing questions across a broad range of topics, including solar-flares, pulsars and the origin of cosmic rays.

5 GLAST Science Instruments Large Area Telescope (LAT) GLAST Burst Monitor (GBM) The GLAST observatory utilizes two main instruments, the large area telescope (LAT) and a GLAST burst monitor (GBM). The GLAST LAT will provide unprecedented sensitivity to gamma rays in the energy range of approximately 20 MeV to 300 GeV. The GLAST burst monitor was selected as a complimentary instrument for the GLAST mission and will be sensitive to X-rays and gamma rays with energies between 8 KeV and 25 MeV. The combination of the GBM and the LAT provides a powerful tool for studying gamma-ray bursts, particularly for time-resolved spectral studies over a very large energy band.

6 GLAST Observatory

7 Delta II 7920H-10 Payload Fairing GLAST spacecraft Second Stage First Stage Solid Motors Fuel Tank Guidance Section Payload Adapter Interstage Centerbody Section First Stage Oxidizer Tank Payload Fairing

8 GLAST Mission Description Launch Site CCAFS SLC-17B Launch Period May 16-Dec 31, 2008 Spacecraft Mass < 4627 kg (10,201 lbs) Launch Time (NET June 3, 2008) 11:45 am EDT Launch Window (NET June 3, 2008) 115 min Launch Azimuth < 28.5 deg Target Orbit (NET June 3, 2008) 565 km circular

9 GLAST Flight Mode Description Delta 7920H-10 launch vehicle with 6915 payload attach fitting and secondary latch mechanism Launch from Cape Canaveral Air Force Station (CCAFS) SLC-17B 94-degree flight azimuth 6/3 solid motor firing sequence Direct flight azimuth mode employed for initial boost phase (combined pitch/yaw) - Quad II-oriented downrange after final solid motor jettison Boost trajectory designed to meet controllability, structural, and environmental constraints while maximizing vehicle performance Main engine cutoff (MECO) occurs at Stage I propellant depletion Stage I-II separation occurs approximately 8 sec after MECO; Stage II ignited 5.5 sec later Payload fairing jettisoned when free molecular heating rate 1135 W/m 2 (0.1 BTU/ft 2 -sec) Stage II first burn places vehicle into 100 X 324-nmi transfer orbit with an inclination of degrees

10 GLAST DTO Trajectory Sequence of Events Event Time (SEC) Liftoff Mach 1 Maximum dynamic pressure 3 Solid motors burnout 3 Solid motors burnout 3 Solid motors ignition Jettison 3 solid motors Jettison 3 solid motors Maximum miniskirt temperature 3 Solid motors burnout Jettison 3 solid motors Begin Quad II down maneuver End Quad II down maneuver MECO Stage I/II separation Stage II ignition Jettison fairing

11 Following the first cutoff of the second stage (SECO 1), the vehicle is reoriented so that centerline is sun-normal - 1 deg/sec roll performed for 48 minutes during coast Reorientation to restart attitude begins at 3642 seconds - Total coast time, from SECO 1 until restart, is ~ 58 minutes 65.1 second restart burn places spacecraft in proper orbit at SECO 2 Vehicle is reoriented for spacecraft separation GLAST Flight Mode Description (cont) Spacecraft separation is approximately 347 seconds after SECO 2 ( seconds after liftoff) - Telemetry coverage from Kwajalein for restart burn and separation Spacecraft separates into a nominal 56-km circular orbit with an inclination of degrees - GVPAT perigee/apogee altitudes based on nmi earth radius

12 GLAST DTO Trajectory Sequence of Events (cont) Event First Cutoff - Second Stage (SECO 1) Begin Reorientation maneuver End Reorientation maneuver Begin BBQ roll maneuver End BBQ roll maneuver Begin Reorientation maneuver Begin Reorientation maneuver Restart 1 Second Cutoff - Second Stage (SECO 2) Spacecraft Separation Time (SEC)

13 GLAST DTO Trajectory Flight Profile* Second Stage Ignition t = sec Alt = 68.9 nmi VI = 20,722 fps MECO t = sec Alt = 64.5 nmi VI = 20,721 fps Payload Fairing Jettison t = sec Alt = 70.3 nmi VI = 20,754 fps FMHR = 0.09 BTU/ft 2 -sec Solid Motor Jettison (3) t = sec Alt = 36.6 nmi VI = 10,623 fps SECO 1 t = sec Alt = nmi VI = 25,930 fps ORBIT: 100 x 324 nmi deg inclination Second Stage Restart t = sec Alt = nmi VI = 24,559 fps Spacecraft Separation t = sec Alt = 301 nmi VI = 24,871 fps ORBIT: 301-nmi circular deg inclination SECO 2 t = sec Alt = nmi VI = 24,874 fps Evasive Burn: t = sec Alt = nmi VI = 24,893 fps ORBIT: 115 x 298 nmi deg inclination Depletion Burn: Safes Stage 2 and lowers orbit inclination Depletion: t = sec Alt = nmi VI = 24,712 fps Liftoff Solid Motor Jettison (6) t = 80.5 / 81.5 sec Alt = 13.5 / 13.8 nmi VI = 3,854 / 3,911 fps SRM Impact SRM Impact ORBIT: 99 x 290 nmi deg inclination *Apogee & perigee altitudes based on nmi Earth radius

14 GLAST DTO Trajectory Orbit Trace Latitude (deg) 75 N 60 N 45 N 30 N 15 N 0 15 S 30 S 45 S 60 S Station Identification TEL = Eastern Range ANT = Antigua KWAJ = Kwajalein HTS = Hawaii Legend (time, sec) 1 = MECO (264.6) 2 = Final IIP (584.4) 3 = SECO 1 (613.8) 4 = Restart (4090.5) 5 = SECO 2 (4155.6) 6 = S/C SEP (4502.5) TEL HTS 6 ANT 5 4 KWAJ 75 S 160 W 100 W 40 W 20 E 80 E 140 E 160 W Longitude (deg)

15 GLAST Flight Mode Description Stage II Evasive and Depletion Burns Following separation, Stage II uses helium retro system to back away from spacecraft Vehicle reorients and then performs 25 second cold gas (nitrogen) evasive maneuver Vehicle reorients again and performs evasive burn - Approximately 6 seconds in duration - Telemetry coverage to be provided from Vandenberg Air Force Base, CA - Perigee lowered to 115 nmi Depletion burn ignition occurs at sec - Telemetry coverage from Antigua tracking station - Nominal duration of 43.9 sec through mono-propellant blowdown - Nominal depletion burn leaves Stage II in a 99 x 290-nmi orbit with an inclination of deg Depletion burn designed to safe stage and lower inclination to minimize casualty probability - Lifetime of Stage II orbit reduced by lowering perigee

16 GLAST DTO Trajectory Sequence of Events Spacecraft separation Begin Stage II retro End Stage II retro Begin reorientation maneuver End reorientation maneuver Begin cold gas evasive maneuver End cold gas evasive maneuver Begin reorientation maneuver End reorientation maneuver Restart 2 (evasive burn) SECO 3 Begin reorientation maneuver End reorientation maneuver Restart 3 (depletion burn) Depletion initiation SECO 4 Event Time (SEC)

17 GLAST DTO Trajectory Stage II Post-separation Orbit Trace 75 N 60 N Station Identification TEL = Eastern Range ANT = Antigua KWAJ = Kwajalein VTS = Vandenberg Latitude (deg) 45 N 30 N 15 N 0 15 S 30 S 45 S 60 S VTS 7,8 Legend (time, sec) 1 = MECO (263.2) 2 = Final IIP (580.8) 3 = SECO 1 (609.6) 4 = Restart (4079.7) 5 = SECO 2 (4161.6) 6 = S/C SEP (4500.0) 7 = Restart (5800.0) 8 = SECO 3 (5805.0) 9 = Restart (6600.0) 10 = SECO 4 (6631.8) TEL 1 ANT KWAJ 75 S 160 W 100 W 40 W 20 E 80 E 140 E 160 W Longitude (deg)

18 Delta II Countdown (T-0 Day)

19 Delta II Terminal Count (T-0 Day)

20 Delta II Operational Flow at Eastern Range Sacramento, CA Magna, Utah L3 Communications Cincinnati Electronics Cincinnati, Ohio communications L3 Communications Space & Navigation Division Budd Lake, NJ CRD RIFCA Graphite-Epoxy Motors ITIP Engine Elkton, MD VAFB RS-27 Engine Star 48 Motor Integration and Checkout Pratt & Whitney Rocketdyne Canoga Park, CA PCM CCAFS Launch Processing Goodrich Aerospace Albuquerque, New Mexico Launch Vehicle Assembly Decatur, Alabama Delta Program Huntington Beach, CA El Paso, Texas Headquarters Littleton, CO Ordnance Shipped Directly to CCAFS From Suppliers Major Subcontractor Major Component Flow Eastern Range CCAFS, Florida

21 Total Vehicle Integration & Checkout at the Launch Site Delta Mission Checkout (Hangar AO) Horizontal Processing Facility First stage from assembly plant Destruct installation Area 55 Second-stage, fairing, interstage from assembly plant Processing Facility Delta II integration and checkout area Receive and inspect Mission integration and checkout Dual composite tests Storage Load on pad erection trailers Destruct installation Erection preparation Leak checks Space Launch Complex 17 Space vehicle Area 59 Mate to upper stage Upper-stage motor Solid motors Balance motor Area 57 Erect and mate stages Install solid motors Check out subsystems Simulated flight test Preflight finalization

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